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引用次数: 0
摘要
本文介绍了位于锥形或平面冲击波后面的通道入口处的气体动力学和流动积分参数的数值研究结果。自由流马赫数范围为 M = 2-4，楔形和锥形压缩面的角度范围为 δ= 10-90°。获得了通道入口处的流动结构、质量平均马赫数、总压力损失系数和流速系数等数据。对这些参数进行了比较分析，并指出了在不同类型的流动中通道入口位置的优缺点。
Numerical simulation of gas dynamics of the inflow into a channel located behind a conical or plane shock wave
The paper presents the results of a numerical study of gas dynamics and integral parameters of the flow at the channel entrance located behind a conical or plane shock wave. The freestream Mach number range is M = 2–4 and the range of the angles of the compression surfaces of the wedge and cone is δ= 10–90°. Data on the flow structure at the channel entrance, mass-averaged Mach numbers, total pressure loss coefficient, and flow rate coefficients are obtained. A comparative analysis of these parameters is performed, and the advantages and drawbacks of the channel entrance positions in various types of the flow are noted.
期刊介绍：
The journal Thermophysics and Aeromechanics publishes original reports, reviews, and discussions on the following topics: hydrogasdynamics, heat and mass transfer, turbulence, means and methods of aero- and thermophysical experiment, physics of low-temperature plasma, and physical and technical problems of energetics. These topics are the prior fields of investigation at the Institute of Thermophysics and the Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences (SB RAS), which are the founders of the journal along with SB RAS. This publication promotes an exchange of information between the researchers of Russia and the international scientific community.
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